Aircraft autorecovery systems and methods

Abstract

Methods and systems for performing auto-recovery for an aircraft. An example system includes position and information systems, an automatic flight control system, a database, and a processor. The database includes terrain data, airport data, obstacle data, and protected airspace data. The processor determines if one of a caution alert or a warning alert exists based on data stored in the database and information received from the position and information systems. Auto-recovery instructions are generated and sent to the automatic flight control system if no positive flight control input has been performed at time of expiration of a waiting period. Auto-recovery instructions are generated based on an analysis of two or more auto-recovery routes. The system does not perform auto-recovery if components of the system fail to meet a predefined validity or integrity level.

1. An apparatus for performing auto-recovery for an aircraft, the aircraft includes position and information systems and an automatic flight control system, the apparatus comprising:
 memory for storing terrain data, airport data, obstacle data, and protected airspace data; and 
 a processor coupled to the memory, the position and information systems, and the automatic flight control system, the processor comprising:
 a component for determining if one of a caution alert or a warning alert exists based on data stored in the memory and information received from the position and information systems; 
 a component for waiting a predefined period of time for positive flight control input by the flight crew; 
 a component for generating two or more auto-recovery routes; and 
 a component for generating an auto-recovery instruction and sending the generated auto-recovery instruction to the automatic flight control system if no positive flight control input has been performed at time of expiration of the waiting period; 
 wherein the component for determining includes a component for setting an integrity flag high or low and wherein the component for generating the auto recovery instruction sends the auto-recovery instruction to the automatic flight control system if the integrity flag is set high. 
 
 
   
   
     2. The apparatus of  claim 1 , wherein the component for analyzing possible recovery routes includes a component for selecting the first analyzed route that is determined to clear the caution or warning alert. 
   
   
     3. The apparatus of  claim 1 , wherein the component for analyzing possible recovery routes includes a component for automatically selecting the recovery route determined to have the best climb gradient. 
   
   
     4. The apparatus of  claim 1 , wherein the component for generating an auto-recovery instruction includes a component for initiating auto-recovery includes a means for increasing flight path angle by 2° if a caution alert is received. 
   
   
     5. The apparatus of  claim 4 , wherein the component for generating an auto-recovery instruction includes a component for initiating auto-recovery includes a means for increasing flight path angle by an additional 2° if the caution alert remains after expiration of an additional waiting period. 
   
   
     6. The apparatus of  claim 1 , wherein the component for setting an integrity flag sets the integrity flag based on validity information produced by the position and information systems and the memory. 
   
   
     7. The apparatus of  claim 1 , wherein the automatic flight control system includes an autopilot system. 
   
   
     8. The apparatus of  claim 1 , wherein the automatic flight control system includes flight control actuators. 
   
   
     9. The apparatus of  claim 1 , wherein the automatic flight control system includes a stick-pusher. 
   
   
     10. The apparatus of  claim 1 , wherein the component for generating an auto-recovery instruction includes a component for initiating auto-recovery includes a means for increasing flight path angle by 6° if a warning alert is received. 
   
   
     11. The apparatus of  claim 1 , wherein the automatic flight control system includes a fly-by-wire system. 
   
   
     12. A system for performing auto-recovery for an aircraft, the system comprising:
 aircraft position and information systems;
 an automatic flight control system; 
 memory comprising terrain data, airport data, obstacle data, protected airspace data and an auto-recovery computer program product; and 
 a processor coupled to the memory, the position and information systems, and the automatic flight control system, the processor comprising:
 a component for determining if one of a caution alert or a warning alert exists based on data stored in the memory and information received from the position and information systems; 
 a component for generating two or more auto-recovery routes; and 
 a component for generating an auto-recovery instruction and sending the generated auto-recovery instruction to the automatic flight control system if no positive flight control input has been performed at time of expiration of a waiting period; 
 
 wherein the component for determining includes a component for setting an integrity flag high or low and 
 wherein the component for generating the auto recovery instruction sends the auto-recovery instruction to the automatic flight control system if the integrity flag is set high. 
 
 
   
   
     13. The system of  claim 12 , wherein the automatic flight control system includes flight control actuators. 
   
   
     14. The system of  claim 12 , wherein the automatic flight control system includes a fly-by-wire system. 
   
   
     15. The system of  claim 12 , wherein the automatic flight control system includes an autopilot system. 
   
   
     16. The system of  claim 12 , wherein the component for analyzing possible recovery routes includes a component for automatically selecting the recovery route determined to have the best climb gradient. 
   
   
     17. The system of  claim 12 , wherein the component for analyzing possible recovery routes includes a component for selecting the first analyzed recovery route that is determined to clear the caution or warning alert. 
   
   
     18. The system of  claim 12 , wherein the component for setting an integrity flag sets the integrity flag based on validity information produced by the position and information systems and the memory. 
   
   
     19. The system of  claim 12 , wherein the automatic flight control system includes a stick-pusher. 
   
   
     20. A computer program product residing on a computer readable medium for generating an auto-recovery instruction for an aircraft, the product comprising:
 a component for determining if one of a caution alert or a warning alert exists based on one or more of terrain data, airport data, obstacle data, and protected airspace data stored in a memory, and information produced by aircraft position and information systems; 
 a component for waiting a predefined period of time for positive flight control input by the flight crew; 
 a component for generating two or more auto-recovery routes; 
 a component for generating an auto-recovery instruction if no positive flight control input has been performed at time of expiration of the waiting period; and 
 a component for sending the generated auto-recovery instruction to an automatic flight control system; 
 wherein the component for determining includes a component for setting an integrity flag high or low and wherein the component for generating the auto recovery instruction sends the auto-recovery instruction to the automatic flight control system if the integrity flag is set high. 
 
   
   
     21. The product of  claim 20 , wherein the component for analyzing possible recovery routes includes a component for selecting the first analyzed route that is determined to clear the caution or warning alert. 
   
   
     22. The product of  claim 20 , wherein the component for analyzing possible recovery routes includes a component for automatically selecting the recovery route determined to have the best climb gradient. 
   
   
     23. The product of  claim 20 , wherein the component for generating an auto-recovery instruction includes a component for initiating auto-recovery includes a means for increasing flight path angle by 2° if a caution alert is received. 
   
   
     24. The product of  claim 23 , wherein the component for generating an auto-recovery instruction includes a component for initiating auto-recovery includes a means for increasing flight path angle by an additional 2° if the caution alert remains after expiration of an additional waiting period. 
   
   
     25. The product of  claim 20 , wherein the component for generating an auto-recovery instruction includes a component for initiating auto-recovery includes a means for increasing flight path angle by 6° if a warning alert is received. 
   
   
     26. The product of  claim 20 , wherein the component for setting an integrity flag sets the integrity flag based on validity information produced by the position and information systems and associated with the terrain data. 
   
   
     27. A method comprising:
 receiving one of a caution alert or a warning alert from a warning system; 
 waiting a predefined period of time for positive flight control input by the flight crew; 
 generating two or more auto recovery routes; and 
 initiating auto-recovery if no positive flight control input has been performed at time of expiration of the waiting period, wherein initiating auto-recovery includes generating two or more auto-recovery routes wherein receiving includes setting an integrity flag at one of a first or second value and wherein initiating initiates auto recovery if the integrity flag is set at the first value. 
 
   
   
     28. The method of  claim 27 , wherein initiating auto-recovery includes increasing flight path angle by 2° if a caution alert is received. 
   
   
     29. The method of  claim 28 , wherein initiating auto-recovery includes increasing flight path angle by an additional 2° if the caution alert remains after expiration of an additional waiting period. 
   
   
     30. The method of  claim 27 , wherein initiating auto-recovery includes increasing flight path angle by 6° if a warning alert is received. 
   
   
     31. The method of  claim 27 , wherein analyzing possible recovery routes includes:
 selecting the first analyzed route that is determined to clear the caution or warning alert. 
 
   
   
     32. The method of  claim 27 , wherein analyzing possible recovery routes includes automatically selecting the recovery route determined to have the best climb gradient. 
   
   
     33. The method of  claim 27 , wherein initiating auto-recovery includes sending flight instructions to an autopilot system. 
   
   
     34. The method of  claim 27 , wherein initiating auto-recovery includes sending control signals to a fly-by-wire system. 
   
   
     35. The method of  claim 27 , wherein initiating auto-recovery includes sending control signals to flight control actuators. 
   
   
     36. The method of  claim 27 , wherein initiating auto-recovery includes sending control signals to a stick-pusher. 
   
   
     37. The method of  claim 27 , wherein the warning system includes an Enhanced Ground Proximity Warning System. 
   
   
     38. The method of  claim 27 , wherein the warning system includes an Enhanced Ground Proximity Warning System and a Protected Airspace Alerting System. 
   
   
     39. A system comprising:
 a means for receiving one of a caution alert or a warning alert from a warning system; 
 a means for waiting a predefined period of time for positive flight control input by the flight crew; 
 a means for generating two or more auto recovery routes; and 
 a means for initiating auto-recovery if no positive flight control input has been performed at time of expiration of the waiting period, 
 wherein the means for initiating auto-recovery generates two or more auto-recovery routes, wherein the means for receiving sets an integrity flag at one of a first or second value and wherein the means for initiating initiates auto recovery if the integrity flag is set at the first value. 
 
   
   
     40. The system of  claim 39 , wherein the means for initiating auto-recovery includes a means for increasing flight path angle by 6° if a warning alert is received. 
   
   
     41. The system of  claim 39 , wherein the means for analyzing possible recovery routes includes a means selecting the first analyzed recovery route that is determined to clear the caution or warning alert. 
   
   
     42. The system of  claim 39 , wherein the means for analyzing possible recovery routes includes a means for automatically selecting the recovery route determined to have the best climb gradient. 
   
   
     43. The system of  claim 39 , wherein the means for initiating auto-recovery includes a means for increasing flight path angle by 2° if a caution alert is received. 
   
   
     44. The system of  claim 43 , wherein the means for initiating auto-recovery includes a means for increasing flight path angle by an additional 2° if the caution alert remains after expiration of an additional waiting period. 
   
   
     45. The system of  claim 39 , wherein the warning system includes an Enhanced Ground Proximity Warning System and a Protected Airspace Alerting System. 
   
   
     46. The system of  claim 39 , wherein the warning system includes an Enhanced Ground Proximity Warning System. 
   
   
     47. The system of  claim 39 , wherein the means for initiating auto-recovery includes a means for sending control signals to a stick-pusher. 
   
   
     48. The system of  claim 39 , wherein the means for initiating auto-recovery includes a means for sending control signals to flight control actuators. 
   
   
     49. The system of  claim 39 , wherein the means for initiating auto-recovery includes a means for sending control signals to a fly-by-wire system. 
   
   
     50. The system of  claim 39 , wherein the means for initiating auto-recovery includes a means for sending flight instructions to an autopilot system.